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Advanced Gas Dynamics NPTEL

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This course introduces the concepts of the primary differences between an incompressible flow and compressible flow. It draws the connection between compressible flow and speed of sound, Mach Number and thermodynamics. It then builds on the governing equations to derive the commonly known equations and tackles both 2D and 3D problems. The physical concept of shocks and the resulting changes in the thermodynamic properties of a fluid form a major part of this course. The course concentrates primarily on the understanding of the physical concepts of compressible flow and keeps reference to various numerical methods for solving the governing equations to a minimum.

Resources: OpenCourseware from NPTEL (India), Sheridan College, MIT, UC Berkeley, Stanford & many other of the World's finest University's.

Language: English

Units: 40

Lesson content

Lec 01-Introduction to Gas Dynamics & Review of Basic Thermodynamics
Lec 02-Review of Basic Thermodynamics Continued
Lec-03 An introduction to Normal Shocks
Lec 04-The Mach Number and Compressible Flow
Lec 05-The relation of physical properties across a normal shock
Lec 06-Normal Shock in a duct: Throat and Reservoir conditions
Lec 07-Example Problems in Normal Shocks
Lec 08-An introduction to Oblique Shocks
Lec 09 The relation of physical properties across an oblique shock
Lec 10-Example Problems in Oblique Shocks
Lec 11-Pressure - Deflection relationship of Shocks
Lec 12-An introduction to Expansion waves
Lec 13-Area - Mach Relationship
Lec 14-Unsteady Shock Waves: The Shock Tube
Lec 15-The Shock Tube: Propagating Normal Shock and its reflection from end
Lec 16-A review of wave propagation
Lec 17-Wave propagation: Small Perturbation Theory
Lec 18-Finite Wave Theory: An introduction to the Method of Characteristics
Lec 19-The Shock Tube: Propagating Expansion Fan
Lec 20-The Method of Characteristics
Lec 21-Application of The Method of Characteristics:
Lec 22-Application of The Method of Characteristics:
Lec 23-Flow over a Wavy wall: Formulation using Perturbation Theory
Lec 24-Subsonic Flow over a Wavy wall
Lec 25-Supersonic Flow over a Wavy wall
Lec 26-Supersonic Flow past a 3D Cone: Axisymmetric/Quasi 2D Flow
Lec 27-Quasi 2D Flow - I
Lec 28-Quasi 2D Flow - II
Lec-29 Similarity Rules and Transformed Coordinate System
Lec 30-Critical Mach Number and Thin Airfoil Theory
Lec 31-Example Problem using Thin Airfoil Theory
Lec 32-Example Problems - 1
Lec 33-Example Problems - 2
Lec 34-Example Problems - 3
Lec 35-Supersonic Flow past a 3D Cone at an angle of attack
Lec 36-Supersonic Flow past a 3D Cone at an angle of attack:
Lec 37-Supersonic Flow past a 3D Cone at an angle of attack:
Lec-38 Supersonic Flow past a 3D Cone at an angle of attack: Governing Equations
Lec-39 Supersonic Flow past a 3D Cone at an angle of attack: Numerical Procedure
Lec-40 Supersonic Flow past a 3D Bluff Body at an angle of attack

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